US12030658B2 - Aircraft control for endurance and fuel economy - Google Patents

Aircraft control for endurance and fuel economy Download PDF

Info

Publication number
US12030658B2
US12030658B2 US17/359,019 US202117359019A US12030658B2 US 12030658 B2 US12030658 B2 US 12030658B2 US 202117359019 A US202117359019 A US 202117359019A US 12030658 B2 US12030658 B2 US 12030658B2
Authority
US
United States
Prior art keywords
airspeed
aircraft
energy consumption
rate
prior
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active, expires
Application number
US17/359,019
Other languages
English (en)
Other versions
US20210403170A1 (en
Inventor
Geoffrey S. M. Hedrick
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
INNOVATION SOLUTIONS & SUPPORT Inc
Innovative Solutions and Support Inc
Original Assignee
INNOVATION SOLUTIONS & SUPPORT Inc
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by INNOVATION SOLUTIONS & SUPPORT Inc filed Critical INNOVATION SOLUTIONS & SUPPORT Inc
Priority to US17/359,019 priority Critical patent/US12030658B2/en
Publication of US20210403170A1 publication Critical patent/US20210403170A1/en
Assigned to INNOVATION SOLUTIONS & SUPPORT, INC. reassignment INNOVATION SOLUTIONS & SUPPORT, INC. ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: HEDRICK, GEOFFERY S.M.
Assigned to INNOVATIVE SOLUTIONS & SUPPORT, INC. reassignment INNOVATIVE SOLUTIONS & SUPPORT, INC. CORRECTIVE ASSIGNMENT TO CORRECT THE ASSIGNEE NAME FROM INNOVATION SOLUTIONS & SUPPORT, INC. TO INNOVATIVE SOLUTIONS & SUPPORT, INC. FOR THE ASSIGNMENT PREVIOUSLY RECORDED ON REEL 060625 FRAME 0750. ASSIGNOR(S) HEREBY CONFIRMS THE ASSIGNMENT. Assignors: HEDRICK, GEOFFERY S.M.
Application granted granted Critical
Publication of US12030658B2 publication Critical patent/US12030658B2/en
Active legal-status Critical Current
Adjusted expiration legal-status Critical

Links

Images

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D31/00—Power plant control systems; Arrangement of power plant control systems in aircraft
    • B64D31/02—Initiating means
    • B64D31/06—Initiating means actuated automatically

Definitions

  • Some aspects of the present subject matter are directed to systems and methods for controlling an aircraft's operating point using closed-loop throttle control, for fuel-efficient flight.
  • Drag 104 is a force that resists the forward motion of aircraft 100 .
  • Drag 104 has a number of components, such as aerodynamic friction between the air and the surface of aircraft 100 (skin friction), aerodynamic resistance to the motion of the aircraft 100 through the air (form drag), and drag caused by lift (induced drag), among others, which are likewise difficult to account for in order to compute drag predictively.
  • drag 104 depends on a number of complex factors, including the size, shape, and weight of aircraft 100 , the surface properties of aircraft 100 , fluid characteristics of the air, and other parameters. Notably, different parameters of drag 104 prevail at different airspeeds.
  • a primary component of drag 104 is the induced drag.
  • lift 102 is generated more easily, and the induced drag actually reduces.
  • the other drag components collectively referred to as parasitic drag, increase.
  • Autothrottle actuator 304 is a parallel subsystem to manual throttle input 302 .
  • Autothrottle actuator 304 automatically regulates the engine power based on command signaling 305 that is generated by autothrottle controller 310 .
  • autothrottle actuator 304 comprises a motor and motor controller, such as a servo motor system, with the rotor of the motor mechanically coupled to manual throttle input 302 .
  • autothrottle actuator 304 is an actuator coupled to the engine(s) or fuel system of aircraft 100 , and may include one or more valves for controlling a flow rate of fuel of combustion air to the engine(s).
  • autothrottle actuator 304 includes one or more switches, transmission gates, or signal amplifiers interfaced with an engine control system of aircraft 100 .
  • autothrottle controller 310 causes autothrottle control system 300 to reduce the airspeed by a first increment.
  • the first increment may be a predefined amount of airspeed, such as ⁇ 2 knots as one example. In various other embodiments, the first increment may be predefined as other values, or it may be dynamically determined based on other factors such as altitude, wing loading, or the like. Accordingly, the engine power is reduced via throttle setting 306 by autothrottle actuator 304 , and airspeed sensor 316 may be monitored under closed-loop control, along with any necessary adjustment of throttle setting 306 to arrive at a new steady state at the newly-reduced airspeed.
  • program 512 tests whether the new rate of energy consumption E NEW is less than the previous (baseline) measurement E CUR . If the result of this comparison is the affirmative case, it indicates that the operating point of aircraft 100 was at an airspeed above the speed associated with the maximum L/D ratio, and the airspeed may need to be further reduced to find the maximum L/D ratio. Accordingly, program 512 branches to operation 612 , where the new rate of energy consumption E NEW is copied to E CUR to become the new baseline value. Further, program 512 loops back to operation 606 , where the airspeed is again reduced by the first increment, followed by operations 608 - 610 .
  • program 512 tests whether the new rate of energy consumption E NEW at the higher airspeed is less than the previous (baseline) measurement E CUR . If the result of this comparison is negative, it indicates that the operating point of aircraft 100 is at approximately the airspeed corresponding to the maximum L/D ratio, meaning that aircraft 100 is at or near its minimum energy utilization and hence at its operating point for maximum endurance. However, if the result of the test at 620 is the affirmative case, this indicates that the operating point of aircraft 100 was at an airspeed below the speed associated with the maximum L/D ratio, and the airspeed may need to be further increased to find the maximum L/D ratio. Accordingly, at 622 , the airspeed is increased by a third increment, such as +2 knots. At this point, aircraft 100 will be operating substantially at its minimum energy utilization point. In the present context, substantially at the minimum energy utilization point means within +/ ⁇ 5% of the minimum energy utilization point under the present operating conditions of aircraft 100 .
  • the process may loop back to 604 to re-run the optimization routine as the prevailing flight conditions may change due to utilization of fuel and lightening of aircraft 100 , changes in altitude, or other factor.
  • This additional cycling of program 512 may be executed continuously, or periodically after passage of a predefined amount of time.

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Combined Controls Of Internal Combustion Engines (AREA)
  • Control Of Vehicle Engines Or Engines For Specific Uses (AREA)
  • Navigation (AREA)
US17/359,019 2020-06-26 2021-06-25 Aircraft control for endurance and fuel economy Active 2042-01-03 US12030658B2 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
US17/359,019 US12030658B2 (en) 2020-06-26 2021-06-25 Aircraft control for endurance and fuel economy

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US202063044801P 2020-06-26 2020-06-26
US17/359,019 US12030658B2 (en) 2020-06-26 2021-06-25 Aircraft control for endurance and fuel economy

Publications (2)

Publication Number Publication Date
US20210403170A1 US20210403170A1 (en) 2021-12-30
US12030658B2 true US12030658B2 (en) 2024-07-09

Family

ID=79032392

Family Applications (1)

Application Number Title Priority Date Filing Date
US17/359,019 Active 2042-01-03 US12030658B2 (en) 2020-06-26 2021-06-25 Aircraft control for endurance and fuel economy

Country Status (5)

Country Link
US (1) US12030658B2 (fr)
EP (1) EP4154098A4 (fr)
JP (1) JP2023533214A (fr)
KR (1) KR20230028367A (fr)
WO (1) WO2021263163A1 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP4284718A1 (fr) * 2021-02-18 2023-12-06 Innovative Solutions & Support, Inc. Interface pilote pour commande d'automanette d'aéronef

Citations (26)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3363480A (en) 1965-10-23 1968-01-16 Bendix Corp Automatic throttle control mechanism
US4312041A (en) * 1978-02-22 1982-01-19 Lear Siegler, Inc. Flight performance data computer system
EP0137610A1 (fr) 1983-08-09 1985-04-17 British Aerospace Public Limited Company Dispositif de commande
US4513235A (en) 1982-01-22 1985-04-23 British Aerospace Public Limited Company Control apparatus
US4516063A (en) 1982-01-22 1985-05-07 British Aerospace Public Limited Company Control apparatus
US4567786A (en) 1982-09-30 1986-02-04 The Boeing Company Modular multi-engine thrust control assembly
EP0265738A2 (fr) 1982-01-22 1988-05-04 British Aerospace Public Limited Company Appareil de commande
US5152360A (en) 1989-07-18 1992-10-06 Eaton Corporation Throttle cable intervention device
US5188316A (en) 1991-12-30 1993-02-23 Dover Corporation Aircraft autothrottle system
US5574647A (en) * 1993-10-04 1996-11-12 Honeywell Inc. Apparatus and method for computing wind-sensitive optimum altitude steps in a flight management system
DE19712153A1 (de) 1997-03-22 1998-10-01 Aeg Sensorsysteme Gmbh Stellantrieb
US6714155B1 (en) * 2003-04-21 2004-03-30 Northrop Grumman Corporation Method of passively estimating an emitter's position and velocity using bearings-only without requiring observer acceleration
US20050150206A1 (en) 2004-01-13 2005-07-14 Snecma Moteurs Throttle control device in particular for turbine aero engine test bench
US6973915B1 (en) 1999-06-11 2005-12-13 Wittenstein Gmbh & Co. Kg Device for controlling an engine
US20070150123A1 (en) 2005-12-08 2007-06-28 The Boeing Company System and method for controlling the airspeed of an aircraft
US20070235594A1 (en) 2006-04-06 2007-10-11 Honeywell International, Inc. Pilot flight control stick feedback system
US20110112705A1 (en) 2009-11-06 2011-05-12 Ratier Figeac Electronic control device for a piloting member with multifunctional microcontrollers, piloting device and aircraft
US20120018578A1 (en) 2010-07-22 2012-01-26 Parker-Hannifin Corporation Near synchronous controlled induction motor drive actuation system
US8195346B1 (en) 2009-01-21 2012-06-05 Garmin International, Inc. Envelope protection for mechanically-controlled aircraft
US8855890B2 (en) 2007-04-18 2014-10-07 Evoke Technology Llc Engine synchronizer
EP2826707A1 (fr) 2013-07-16 2015-01-21 McCulloch, Norman L Système de rétroaction pour un élément de commande de vol
US20180286253A1 (en) 2017-03-31 2018-10-04 General Electric Company Optimized aircraft control via model-based iterative optimization
US10099795B2 (en) 2015-11-04 2018-10-16 Innovative Solutions & Support, Inc. Precision operator for an aircraft autothrottle or autopilot system
US20180366010A1 (en) 2007-12-10 2018-12-20 Leedor Agam System for producing a flight plan
US20190047715A1 (en) 2015-11-04 2019-02-14 Geoffrey S.M. Hedrick Precision Operator for an Aircraft Autothrottle or Autopilot System with Engine Performance Adjust
US20190055028A1 (en) 2016-03-10 2019-02-21 The Boeing Company Automated flight throttle control

Patent Citations (27)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3363480A (en) 1965-10-23 1968-01-16 Bendix Corp Automatic throttle control mechanism
US4312041A (en) * 1978-02-22 1982-01-19 Lear Siegler, Inc. Flight performance data computer system
EP0265738A2 (fr) 1982-01-22 1988-05-04 British Aerospace Public Limited Company Appareil de commande
US4513235A (en) 1982-01-22 1985-04-23 British Aerospace Public Limited Company Control apparatus
US4516063A (en) 1982-01-22 1985-05-07 British Aerospace Public Limited Company Control apparatus
US4567786A (en) 1982-09-30 1986-02-04 The Boeing Company Modular multi-engine thrust control assembly
EP0137610A1 (fr) 1983-08-09 1985-04-17 British Aerospace Public Limited Company Dispositif de commande
US5152360A (en) 1989-07-18 1992-10-06 Eaton Corporation Throttle cable intervention device
US5188316A (en) 1991-12-30 1993-02-23 Dover Corporation Aircraft autothrottle system
US5574647A (en) * 1993-10-04 1996-11-12 Honeywell Inc. Apparatus and method for computing wind-sensitive optimum altitude steps in a flight management system
DE19712153A1 (de) 1997-03-22 1998-10-01 Aeg Sensorsysteme Gmbh Stellantrieb
US6028280A (en) 1997-03-22 2000-02-22 Aeg Sensorsysteme Gmbh Actuator for generating switching signals
US6973915B1 (en) 1999-06-11 2005-12-13 Wittenstein Gmbh & Co. Kg Device for controlling an engine
US6714155B1 (en) * 2003-04-21 2004-03-30 Northrop Grumman Corporation Method of passively estimating an emitter's position and velocity using bearings-only without requiring observer acceleration
US20050150206A1 (en) 2004-01-13 2005-07-14 Snecma Moteurs Throttle control device in particular for turbine aero engine test bench
US20070150123A1 (en) 2005-12-08 2007-06-28 The Boeing Company System and method for controlling the airspeed of an aircraft
US20070235594A1 (en) 2006-04-06 2007-10-11 Honeywell International, Inc. Pilot flight control stick feedback system
US8855890B2 (en) 2007-04-18 2014-10-07 Evoke Technology Llc Engine synchronizer
US20180366010A1 (en) 2007-12-10 2018-12-20 Leedor Agam System for producing a flight plan
US8195346B1 (en) 2009-01-21 2012-06-05 Garmin International, Inc. Envelope protection for mechanically-controlled aircraft
US20110112705A1 (en) 2009-11-06 2011-05-12 Ratier Figeac Electronic control device for a piloting member with multifunctional microcontrollers, piloting device and aircraft
US20120018578A1 (en) 2010-07-22 2012-01-26 Parker-Hannifin Corporation Near synchronous controlled induction motor drive actuation system
EP2826707A1 (fr) 2013-07-16 2015-01-21 McCulloch, Norman L Système de rétroaction pour un élément de commande de vol
US10099795B2 (en) 2015-11-04 2018-10-16 Innovative Solutions & Support, Inc. Precision operator for an aircraft autothrottle or autopilot system
US20190047715A1 (en) 2015-11-04 2019-02-14 Geoffrey S.M. Hedrick Precision Operator for an Aircraft Autothrottle or Autopilot System with Engine Performance Adjust
US20190055028A1 (en) 2016-03-10 2019-02-21 The Boeing Company Automated flight throttle control
US20180286253A1 (en) 2017-03-31 2018-10-04 General Electric Company Optimized aircraft control via model-based iterative optimization

Non-Patent Citations (8)

* Cited by examiner, † Cited by third party
Title
http://www.eaa1000.av.org/technicl/perfspds/perfspds.htm.
https://en.wikipedia.org/wiki/Lift-to-drag_ratio.
https://www.flyingmag.com/very-best-speed-fly/.
https://www.grc.nasa.gov/www/k-12/airplane/ftime.html.
https://www.grc.nasa.gov/www/k-12/airplane/ldrat.html.
Roh'lix ® Linear Actuators Binsdocid: XP 55492757A Mar. 26, 2017 4 pages.
Search Report and Written Opinion dated Sep. 30, 2021 issued in International Patent Application No. PCT/US21/39182.
Search Report dated Apr. 11, 2024 issued in European Patent Application No. 21828331.5.

Also Published As

Publication number Publication date
EP4154098A4 (fr) 2024-05-15
EP4154098A1 (fr) 2023-03-29
WO2021263163A1 (fr) 2021-12-30
JP2023533214A (ja) 2023-08-02
KR20230028367A (ko) 2023-02-28
US20210403170A1 (en) 2021-12-30

Similar Documents

Publication Publication Date Title
US6171055B1 (en) Single lever power controller for manned and unmanned aircraft
US9932120B2 (en) Method and apparatus for controlling a turboprop engine
US10112723B2 (en) Method and a device for stopping a turboshaft engine in nominal operation
US9488054B2 (en) Method of automatically regulating a rotorcraft power plant, a rotorcraft power plant, and a rotorcraft
CN110001973B (zh) 轻型固定翼无人机的混合动力推进系统与控制方法
EP0092501B1 (fr) Commande de moteur d'hélicoptère économisant du carburant en croisière
US9475572B2 (en) Propeller operation
CN105867121A (zh) 用于自旋恢复的直升机非线性预测控制方法及装置
CN112594069B (zh) 基于功率需求预测的涡轴发动机抗扰控制方法及装置
US12030658B2 (en) Aircraft control for endurance and fuel economy
US12078111B2 (en) Systems and methods for determining and/or controlling motor thrust and engine thrust in a parallel hybrid aircraft
CN111919018B (zh) 用于涡桨发动机的螺旋桨速度超调限制的控制系统和方法
CN210882651U (zh) 轻型固定翼无人机的混合动力推进系统
CN117807916B (zh) 一种喷气式飞机给定推力最大航程巡航设计方法
CN117807915B (zh) 一种喷气式飞机给定重量最大航程巡航设计方法
Barufaldi et al. Optimal climb performance of electric aircraft for minimal charge consumption
Tang et al. Propulsion system optimization for the tail-sitter VTOL SUAV
Hanås et al. Off-design performance modelling of a propfan aero engine. An off-design performance evaluation of a notional engine design for future reductions in fuel consumption and emissions
CN118092163A (zh) 一种基于飞推一体化模型的综合控制方法
Scherrer et al. 23. NASA-LOCKHEED SHORT-HAUL TRANSPORT STUDY
Caldwell et al. The Constant-Speed Propeller: Part I-Its Performance
STEILS JR V/STOL hover control system analysis

Legal Events

Date Code Title Description
FEPP Fee payment procedure

Free format text: ENTITY STATUS SET TO UNDISCOUNTED (ORIGINAL EVENT CODE: BIG.); ENTITY STATUS OF PATENT OWNER: SMALL ENTITY

FEPP Fee payment procedure

Free format text: ENTITY STATUS SET TO SMALL (ORIGINAL EVENT CODE: SMAL); ENTITY STATUS OF PATENT OWNER: SMALL ENTITY

STPP Information on status: patent application and granting procedure in general

Free format text: DOCKETED NEW CASE - READY FOR EXAMINATION

AS Assignment

Owner name: INNOVATION SOLUTIONS & SUPPORT, INC., PENNSYLVANIA

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNOR:HEDRICK, GEOFFERY S.M.;REEL/FRAME:060625/0750

Effective date: 20220725

STPP Information on status: patent application and granting procedure in general

Free format text: NON FINAL ACTION MAILED

AS Assignment

Owner name: INNOVATIVE SOLUTIONS & SUPPORT, INC., PENNSYLVANIA

Free format text: CORRECTIVE ASSIGNMENT TO CORRECT THE ASSIGNEE NAME FROM INNOVATION SOLUTIONS & SUPPORT, INC. TO INNOVATIVE SOLUTIONS & SUPPORT, INC. FOR THE ASSIGNMENT PREVIOUSLY RECORDED ON REEL 060625 FRAME 0750. ASSIGNOR(S) HEREBY CONFIRMS THE ASSIGNMENT;ASSIGNOR:HEDRICK, GEOFFERY S.M.;REEL/FRAME:063743/0759

Effective date: 20220725

STPP Information on status: patent application and granting procedure in general

Free format text: RESPONSE TO NON-FINAL OFFICE ACTION ENTERED AND FORWARDED TO EXAMINER

STPP Information on status: patent application and granting procedure in general

Free format text: EX PARTE QUAYLE ACTION MAILED

STPP Information on status: patent application and granting procedure in general

Free format text: RESPONSE TO EX PARTE QUAYLE ACTION ENTERED AND FORWARDED TO EXAMINER

STPP Information on status: patent application and granting procedure in general

Free format text: NOTICE OF ALLOWANCE MAILED -- APPLICATION RECEIVED IN OFFICE OF PUBLICATIONS

STPP Information on status: patent application and granting procedure in general

Free format text: AWAITING TC RESP., ISSUE FEE NOT PAID

STPP Information on status: patent application and granting procedure in general

Free format text: NOTICE OF ALLOWANCE MAILED -- APPLICATION RECEIVED IN OFFICE OF PUBLICATIONS

STPP Information on status: patent application and granting procedure in general

Free format text: PUBLICATIONS -- ISSUE FEE PAYMENT VERIFIED

STCF Information on status: patent grant

Free format text: PATENTED CASE